Missile with separable components



May 12, 1964 R. HALL MISSILE WITH SEPARABLE COMPONENTS 5 Sheets-Sheet 1Filed 001;. 18, 1954 INVENTOR. RANDOLPH F. HAL;

BY GMQ M MTQW,

ATTORNEYS.

May 1 -1964 R. F. HALL MISSILE WITH SEPARABLE COMPONENTS 5 Sheets-Sheet2 Filed Oct. 18, 1954 {El IN:

INVENTOR. RANDOL PHI-T HALL A T7'OPNEYS.

HHHI

May 12, 1964 R. F. HALL MISSILE WITH SEPARABLE COMPONENTS 5 Sheets-Sheet5 Filed Oct. 18, 1954 7 M2 Q @g lvllllhvt IN V EN TOR.

A i @Qfi 6 RANDOLPH E HALL BY wam wfim,

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May 12, 1964 R. F. HALL MISSILE WITH SEPARABLE COMPONENTS 5 SheetS-Sheet4 Filed Oct. 18, 1954 INVENTOR. I RANDOLPHEHALL amampzww m A TTORNEYSMay 12, 1964 R. F. HALL 3,132,590

MISSILE WITH SEPARABLE COMPONENTS Filed Oct. 18, 1954 s Sheets-Sheet SMISSILE WITH SEPARABLE COMPONENTS Randolph F. Hall, Buffalo, N.Y.,assignor, by mesne assignments, to Bell Aerospace Corporation,Wheatfield, N.Y., a corporation of Delaware Filed Oct. 18, 1954, Ser.No. 462,743 Claims. (Cl. 102-49) -This invention relates to air-to-air,supersonic, semiactive homing, solid fuel rocket-launched and propelledmissiles. Such a missile may beconsidered as comprising, as generalcomponent parts thereof, an airframe, an autopilot, a seeker, a boosterrocket, a sustainer rocket,

war head and fuse components, hydraulic and electrical" poweringdevices; and in some cases special accessories sile' structure, outwhich separates automatically from the missile at the end of the boostphase of the missile Q flight. 'The flight phaseis maintained by aseparate solid propellant fuel typelsustainer rocket engine comprisinganother component of the missile structure. Guidance to the target isobtained'by means of a semi-active inter ferometer homing system; thetarget being illuminated by the radar broadcaster of the launchingaircraft.

While the missile is mounted on the launcher pylon I of the aircraft,connections are made with pre flight checking and launcher actuatingdevices controlled from within the aircraft and powered by sourcesexternal of the missile. During the boost phase'of missile flight,controlfand stability are obtained'by the missile autopilot 'systemuntil the target seeker or homing controls .take oven.

At the end of the boost phase of the missile flight the. boost enginecomponent of the missile separatesand falls away from the missile inresponse to operation of a separation switch functioning in response tolowering cine boost rocket chamber pressure. closes an electricalcircuit to a detonator which energizes a -pair of explosion bolts, the.destruction of which releases the boost section of the missilefrom theremainder.

Itis 'a particular object of the present invention to provide a missileas aforesaid embodying maximum operational reliability. 2

Another object of the invention is to provide a missile 'as aforesaidpossessing operating and control characteristics providing maximumsafety for the handling personnel and equipment.

' Another object of the invention is to provide a missile as aforesaidhaving improved performance and accuracy characteristics in itsoperation.

Anotherobject of the invention isto provide a missile as aforesaidwherein the constructional components are, as nearly as possible, ofstandard form and readily adapted to existingor planned logisticalsupport equip ment; thereby facilitating maintenance, testing, andoperation. I p

, Another object of the invention is to provide a mis: sile as aforesaidcomprising an assembly of components readily adapted to be stored andtransported to flight basepoints with maximum facility.

Another object of the invention is to provide a missile I "United StatesPatent ,0 ice The switch then as aforesaid wherein the component partsare adapted tov be rapidly assembled and mounted'relative to thelauncher equipment with greatly improved facility.

Another object of the invention is to provide a missile as aforesaidwhichis of reduced weight compared to.

prior missile designs, without sacrifice of desired per formancecharacteristics. By way of exemplification of the invention a missileembodying the features thereof is illustrated in the accompanyingdrawings wherein: p FIG. 1 is a side elevational view thereof;

FIGS. 2, 3, 4 are sectional views taken along lines 'II-II, III-Ill,IV1V of FIG. 1; i

line VIIIVIII of FIG. 6;

FIG. 9 is a fragmentary side elevation, partly insection,'of thewar-head section of the missile;

' FIG. '10 is a sectional view taken along line X-X of,

FIG. 9;

FIG. 11 is, an end elevational view taken along line FIG. 12 is afragmentary. sectional view taken along line XII'XII of FIG. 1; 7 FIG.l3 is a fragmentary sectional view taken along line XIIIXIII of FIG. 12;

FIG. 14 is a fragmentary rear end view of the booster section of themissile of the invention; and

FIG. 15 is a fragmentary sectional view taken along line XV-XV of-FIG.14-. 7

As shown in FIG. 1, the missile of the invention may be convenientlysectionalizedfunctionally as comprising a forward section; va centersection; and'an aft section which includes a sustainer engine section.The forward section contains a seeker mechanismas indicated at 20 (FIG.1); the forward flight control vanes 46; and the forward hydraulic orother power. supply mechanism The center sectioncontainsthe war head 24,or in lieu thereof telemetering mechanism for transmission ofperformancedata during flight. The aft sectionconveniently contains thegyros 26, autopilot electronic mechanisms '28, and the airfoil controls94 at the aft end of the missile. .It also may conveniently contain 50.

rocket engine 30 is housed in the sustainer section at the rear end ofthe aft section. For launching or booster purposes a booster rocketsection as indicated at 90 is temporarily attached to the rear of thesustainer section of the missile, as will be explained more fullyhereinafter. p

The's eeker system of the missile is a semi:active phase comparisonradar seeker designed to home on target radar-echo signals. The targetillumination is" provided 7 I by radar from the launching aircraft. Theseeker obtains a'measure of the angular velocity of line of sight to thetarget, "by measuring the relative phase rate of signals received atspaced antennas designated 40 mounted on the tips of the missile canardvanes 42. one pair of antennas relates to control of the craft in pitch,while the other pair relates to the yaw control. The

information received by the antennas is convertedinto sensed voltage forthe autopilot mechanism. This sensed voltage is supplied to theautopilot as an error Patented Ma 12, 1964 v signal and is proportionalto the approximate algebraic difference of the angular velocity of theline of sight relative to the missile longitudinal axis, and of theangular velocity of the missile. The autopilot system is automaticallycapable of operating throughout a wide range of altitudes. The pitch andyaw system is based on the rate gyro-accelerometer arrangement so as toprovide inherent compensation for altitude variations. Accelerationlimiting to prevent destructive maneuvers of the missile (in excess of15 Gs) in either plane is preferably incorporated, as are provisions tolimit the angle of attack of the missile at higher altitudes, say above30,000 feet, to prevent the possibility of missile tumbling. This may beaccomplished by utilizing pressure sensitive devices to decrease the Glimiting settings, as a function of altitude. The roll system issubstantially conventional and includes automatic altitude compensationto change the system gain as a function of pressure altitudes.

The design is such that all sections can be completely assembled withunusual rapidity; for example, within two minutes. Therefore, allmechanical, hydraulic, pneumatic, and electrical connections between therespective sections are the quick coupling type, and are designed toeliminate possibilty of mis-connections.

As shown in better detail in FIGS. 5, 6, 7, 8, the forward section ofthe missile comprises generally a tapering profile body portion 44 whichmounts four radially extending planes 42 which are fixed to the missilebody,

and which carry at their outer ends the radar reflection antenans 40,previously referred to. The vanes 42 are each supplemented by movableflaps 46 for control of the flight direction in both pitch and yaw;operation of the pitch and yaw control flaps 46 being automatic and inresponse to operation of the seeker mechanism, as

explained hereinabove.

Whereas, it is well known that a seeker system designed to home ontarget radar-echo type signals may be employed to actuate flight controldevices such as the vanes 46 in order to guide such a missileconsistently toward the target, it is afeature of the present inventionthat the vanes 46 are mounted upon the airframe structure andconstructed and arranged as shown in the drawing herewith so as tofacilitate design and construction and operation of the missile of theinvention in improved manner. For example, as shown in FIGS. -8, thevanes 46 are each provided with integral stub shaft portions 43 whichterminate in splined end portions 49 which slip-fit in the case ofoppositely paired vanes, in keyed relation into opposite end portions ofa cross shaft 50. The cross shafts 5050 interconnecting the oppositelydisposed vanes of the movable flap control system are arranged to rotateabout longitudinal axes intersecting at point 51; and in order to permitthe cross shaft devicesStl-Sil to be so arranged the shafts are both cutaway as indicated at 52 and beveled as indicated at 53. Thus, asillustrated diagrammatically in FIGS. 7-8, the shafts 50-50 are eachfree to rotate as much as 50 between the positions thereof shown in FIG.7 and in FIG. 8 Without interference with one another, even though thelongitudinal axes thereof intersect and coincide as indicated at 51.

In order to power the cross shafts 50-50 for flight controlmanipulations of the flaps 46, the shafts 50 are provided with controlhorns 56, 57 respectively; the horns 56, 57 being connected as indicatedat 59, 59 to suitable push-pull control devicesleading to theseeker-actuated control mechanisms referred to hereinabove. Thus, byvirtue ofthis arrangement of parts, the vanes 46 extending in rightangular relation radially of the body 44 are pivoted upon axes containedin a common plane transverse to the body of the missile, for optimumpitch and yaw control purposes. 7

Furthermore, it is a feature of the constructional arrangement of theinvention that the flight control vanes 46 may be exchanged and replacedfrom time to time, without disturbance of the antenna devices 40 (theprecise settings of which are critical to proper operation of the entiremechanism). For this purpose installation and/or replacement of thecontrol flaps 46 is provided for by constructing the control flap ineach case to comprise a main fiap portion 46 which is bolted asindicated at 62 to a base flap portion 64 which is formed integral withthe stub shaft 48 previously referred to. A machine screw 66 in linewith axis of the stub shaft portion 48 locates the outboard end portionof the flap device 46-64 and provides .in conjunction with the stubshaft portion 48 a pair of spaced pivotal mountings therefor. The outerflap portion 46 is shaped to include a cut-out portion as indicated at67 (FIG. 5) which complements the plan form shape of a counterboredblock 68 bolted to a U sectioned bracket 68a by means of machine screws69. The bracket 68a is in turn bolted to vane 42; and the antenna 40 iswelded or otherwise fixed to the bracket 68a.

Thus, it will be understood that in order to assemble and/or disassemblethe movable flap structures from the fixed structure of the missile, itis only necessary to initially withdraw the machine screws 62 and 69whereupon the flap portion 46 is disconnected from the fixed structureof the aircraft. Hence, in the field, control flaps of various shapesand/or dimensions as prescribed by contemplated tactics, may be readilyinstalled with maximum facility without disturbances to the previouslyaligned antennas 40 relative to the flight axis of the missile.

As stated hereinabove, it is a primary object of the present inventionto provide the missile structure so as to be readily adapted torelatively rapid assembly of the component parts at field stations withminimum diificulty. Thus, for example, the section of the missileidentified in FIG. 1 within the broken boundry line designated IXcomprises a tubular body section 70- interiorly of which may bemounted awar head load; or in event the missile is to be employed for observationor experimental purposes or the like, the body section 70 may mounttherewithin any desired complement of instruments, such as telemeteringequipment as explained hereinabove. Hence, it is contemplated that thestorage depots in the field adjacent launching or air flight base depotswill stock supplies of sections 70 containing alternatively suchloadings as may be called for from time to time.

In order to enable the ground crew to quickly assemble a missileincluding prescribed components, the body section '70 is provided at itsopposite ends with quick-connect fastening devices for engagement withthe forward body portion 44 and the central body section 75 (FIGS. J1and 9). The cooperating end portions of the shell members 4475 areprovided with rigidly mounted end flange members as indicated at 76(FIG.-9); the flanges 76 being fixed to the shell portions 4475 by meansof machine screws as indicated at 77. The outer ends of the flange rings76 are formed to reduced diameters and externally threaded as indicatedat 78 to accommodate thereon in screwthreaded relation a locking ring80. The rings 80 are formed with interrupted flanges as indicated at 82for cooperation with complementary shaped interrupted flange portions 84carried by a mounting ring 85 which is fixed to the casing sec-tion 70by means ofmachine screws as indicated at 86.

Thus, to relatively assemble the casing parts, the casing member 70 issimply slip-fitted into assembled position as shown in FIG. 9; thelocking rings 80 having been previously screwthreaded onto the casingportions 44 and 75. The locking rings are then rotated approximatelyone-eighth of a revolution, thereby bringing the flange portions 82-84into mutually abutting relation for locking the casing parts againstdisassembly displacements. The rings 80 are formed with drilled openingsas indicated at 88 to permit a wrench or plybar to be inserted Setscrews 89 are preferably carried ing sections together against relativerotation incidental to rotation of the locking rings80. A set screw 89amay 7 be provided for locking the ring 80 in holding position.

f The casing section 75 encloses a solid propellant fueltype'flightsustainer rocket engine, which of course may be of anypreferred design and housed within the casing section 75 so as todischarge through a nozzle at the rear end thereof to maintain in flightthe missile structure comprising the sections 44, 70', 75, subsequent todetachment therefrom of the booster rocket engine section which isenclosed within a casing portion 90. Thus, subsequent to detachment ofthe booster section 90, the casing portion 75 constitutes the rear endportion of the missile in sustained flight, and as illustrated in FIGS.1, 3, this will be operatively arranged to be actuated by means ofIanypreferred electrical'or hydraulic control systems are in turnenergized by automatically functioning mechanisms responsive to signalsreceived from the seeker mechanism and/or from the auto pilot mechanismenclosedwith'in the machine.

QTo permit the booster end section of the entire missile 1 to be quicklydisconnected and released from the forward and 'centerlsections thereofat the end of the boost phase dicated generally by the numeral 100, andcomprises a pair of C-shaped yoke members 102 104' Each such yoke memberis provided with an apertured ear 106 carrying one end of an explosivebolt 108, the other end of which is screwthreaded into a bracket 110which pivotally connects as indicated at 111 to the other end of thecorresponding yoke piece. Thus, when the parts are relatively assembledas illustrated in FIG. 12, they complete aring-like structure encirclingthe missile body; and as 7 shown in FIG. 13, the connection ring isdisposed so as to overlie the abutting junction between the center andaft sections 75, 90 of the missile.

At this point of juncture, the casing sections 75, '90 are each formedwith r outwardly extending radial flanges 112, 114 respectively, and theyoke parts 152, 104 of the connecting ring unit are grooved as indicatedat 116 with beveled side edges as indicated at 118, whereby clamping ofthe yoke parts The connection device referred to is in- It is however afeature of the present invention that the supporting yoke parts 102, 104are normally maintained in connected relation as shown in FIG. 12 bymeans of a pair of explosive bolts as indicated at;100-- 108. Thesebolts may of course be of any preferred design but essentially comprise!threaded machine screw type devices internally bored to accommodatetherein explosive charges as indicated at 126; the bolt diameters beingreduced in the regions of the explosive charges 126 and at positionsclear of the mounting bracket parts 106, 1-10. Suitable detonatingdevices as indicated at 128 are also provided in the explosive carryingbores, and are arranged'to be energized, as by means of detonatorconductors 130. Energization of the detonators may be accomplished' inany preferred manner; but it is herein contemplated that they will bedevices which are in turn actuated in response to operation of apressure change responsive bellows 131 interiorly of the combustionchamber section of thebooster engine 132 (FIG. 1,) located within thecasing portion 90.

Thus,.as the fuel of the'booster engine section becomes dissipated, andthe booster engine power falls off, reduction in pressure withinthecombustion chamber thereof decreases so as to cause the detonators128-428 to be energized, thereby causing the bolts 108-408 to beruptured upon explosion of the charges 126 therewithin. This releasesthe lower-yoke portion 104 from the upper yoke portion, therebypermitting the aft section of the missile to fall away from thesustained flight portion thereof. At this moment, the rocket enginemounted within the casing section 75 is started automaticallyin responseto control mechanism, as indicated at 134 (FIG. 1). The starter 134 maybe energized by the same circuit which detonates the bolts 108, or maybe controlled by any other device such as by separation of the boostersection from the main section; and in any case the control may be of anypreferred form and does not per se comprise a part of.

the present invention.

102, 104 in the operative position as shown in FIGS. 12,

13 will [firmly press together and maintain the casing parts in'theassembled relation as shown. In order 'to insure proper alignment of thefins of the booster section 90 with the fins 02 of the missile, whenbeing assembled in-theffield, the flange 114 is formed with a rewss toreceive the head'of a screw 119 mounted in the clamp ring .104; thusassuring proper indexing of the missile section parts.

The uppermost yoke member 102 is formed with a C- shaped bracket device120 which is arranged to grip upon the bracket devices 122- 122extending downwardly from the mounting airplane structure, whereby uponlaunching of the missile it will simply slide forwardly on thesupprovided with another knob-like slide fitting deviceas inheated at124 (FIGS. 1, 3); it being understood that the launching and latchrelease mechanisms incidental to the'supporting bracket device s 120-124 may be of any preferredjform, and do not form parts of the presentinvention, per se.

Because of the provision of a pair of explosive bolts 108, 108, properoperation of, the disconnect mechanism is assured, although experiencehas proven that there is always some risk thatan explosive bolt of thistype may not adequately function. Thus, in the case of the presentinvention if either one of the bolts as indicated at 108,

108 fires properly and is thereby disrupted, the boost section of themissile will 'be disconnected from the flight section at the end of theboost phase of the missile flight, eventhough the other bolt may havefailed to. explode.

For stabilization of thefboost phase of the missile flight,

a plurality, of fixed vanes as indicated at are mounted to extendradially from the rear end portion of the casing section 90. Anotherparticular feature of the present invention resides in the method forquickly mounting the vanecomponents 140 on the tail end portion of themissile preliminary to flight operation.

'As shown in greater detail in FIGS. l4-15, novel arrangement is madefor mountingthe booster section fin installations as subaassembly unitsto the rear end of the casing section 90. This'section includes as anintegral structural portion thereof, .the booster rocket enginedischarge nozzle component which includes a throat flange portion asindicated at 144; a constricted venturi throat portion 145; and a blastdischarge funnel-shaped end portion 146, as is conventional in the art.It is of course to be understood that this rocket engine nozzlestructure as referred to hereinaboveis a conventional component of therocket engine per se forming no part of the present this mounting ring150 is so dimensioned as to slip-fit over the rear end 146 of the enginenozzle, and then when it is bolted in position against the flange 144 bymeans of the screws 152, an annular space is provided around outside thering 150 to accommodate in slip-fitted mounted relation thereon theengine nozzle shroud or shell as indicated at 155. The shroud 155 isthen fixed to the mounting ring 150 by means of machine screws 156.

For convenience in installation, the shroud element 155 is preferablyfabricated in the form of two half shell sections joined together bymeans of diametrically opposed scab plates as indicated at 158158 (FIGS.14-15 the splice plates l58158 being fixed to the shroud pieces by meansof machine screws as indicated at 159. Thus, the shroud element 155encloses the rocket engine nozzle and completes the streamlined profileconfiguration of the overall missile body.

The shroud plates are apertured as indicated at 160 (FIG. 15) toaccommodate in slip-fitted relation therethrough the root end portions162 of the spar components 164 of the booster section fin structureswhich are designated generally by the numerals 140; the fin structuresincluding transverse base plates 166 and radially extending airfoilstructures 168, in addition to the spar elements 164. To secure the fins140 to the shroud shell 155, anchoring blocks 170 are mounted interiorlyof the shell plates 55 by means of machine screws 172. The blocks 170are centrally apertured as indicated at 173 in registry with theapertures 160 through the shroud plates 155, so as to accommodate theroot end portions 162 of the fin spars when slip-fitted thereinto asshown in FIGS. 14-15.

To lock the fin structures relative to the shroud 155, locking pins 175are slip-fitted through registering apertured portions of each block 170and its corresponding fin spar 162 (FIG. 15); the pins being then lockedin holding positions by manual rotation of their outer bent end portions176 downwardly into holding slots 178 formed in the shell 155. Thus, itwill be readily appreciated that the integral fin sub-assembliesincluding the spar and base and fin structures 164-, 166, 168 may bequickly mounted on the missile booster section by slipfitting the rootend portions of the spar elements into the mounting blocks 170 and thenlocking the fins in place by means of the locking rods 175, whereuponthe unit is ready for operation with a minimum of on-the-field assemblyproblems. It will also be apparent that by virtue of this arrangementthe fins are located at the immediate rear end portion of the boostersection of the missile, for most eflicient aerodynamic tflght controlpurposes, through use of a rugged yet simplified detachable connectionwith the shroud element enclosing the rocket engine nozzle.

I claim:

1. In an air missile construction, a streamline shaped body, a flightcontrol vane structure comprising a fixed fin extending radially of saidbody, a channel sectioned bracket embracing and fixed to the outboardend of said fin and extending rearwardly thereof, a target seekingantenna device of elongated form fixed to the outer side portion of saidbracket to extend parallel to said body, a bearing block detachablybolted to said bracket, and having a hinge pin extending inwardlytherefrom, a stub shaft rotatably mounted within said body and connectedtherein to a flap control device and extending outwardly therefrom, anda flight control flap fixed at one end tosaid hinge pin and detachablybolted to said stub shaft.

2. In an air missile construction, a streamline shaped body, a flightcontrol vane structure comprising a fixed fin extending radially of saidbody, a bracket fixed to the outboard end of said fin and extendingrearwardly thereof, a target seeking antenna device fixed to saidbracket, a bearing block detachably bolted to said bracket and having ahinge pin extending inwardly therefrom, a stub shaft rotatably mountedwithin said body with its axis of rotation aligned with said hinge pinand connected to a flap control device, and a flight control flap fixedat one end to said hinge pin and detachably fixed to said stub shaft atits opposite end.

3. In an air missile construction, a tubular casing member, a rocketengine disposed within said casing and having a funnel-shaped jetdischarge nozzle extending therefrom through the rear end portion ofsaid casing, a nozzle shrouding sleeve comprising a pair ofsemi-cylindrical sleeve half portions bolted together and detachablyconnected to the rear end of said casing to enclose said nozzle, saidsleeve having a plurality of fin mounting blocks bolted interiorlythereof at intervals peripherally of said sleeve, said sleeve and saidblocks being apertured in mutual alignments thereby providing socketsdirected radially of said sleeve, and a plurality of vane devices eachcomprising a fin portion and an extending spar root portion adapted toslip-fit into either of said sockets, and manually operable pin meansslidable into registering longitudinal openings in said blocks and saidspar root portions to detachably lock said vane devices in operativepositions radially of said sleeve.

4. In an air missile construction, a tubular casing member, a rocketengine disposed within said casing and having a funnel-shaped jetdischarge nozzle extending through the rear end portion of said casing,a nozzle shrouding sleeve detachably connected to the rear end of saidcasing to enclose said nozzle, said sleeve having a plurality of finmounting sockets therein directed radially of said casing, and aplurality of interchangeable aerodynamic fin devices adapted to slip-fitat their root ends into said sockets, and manually operable lock meansextending exteriorly of said sleeve for detachably locking said findevices to said sleeve.

5. In an air missile, the combination of a streamlined elongatedtwo-part body including a main missile section and a flight boostersection and detachable connection means adapted to couple together saidmain and booster Sections, said main section comprising separate foreand aft portions and an intermediate portion and means detachablymounting said intermediate portion between said fore and aft portions,said fore portion mounting fixed fins extending therefrom and mountingat their outer ends fixed target seeking antenna devices, flight pathguide flaps hingedly connected to said fixed fins, said intermediateportion containing a war head device, said aft portion mounting fixedfins and flight control flaps for cooperation with said first mentionedfins and flaps to guide said main missile body section in flight, saidbooster section having adjacent its rear end fixed fin type flightguidance vanes detachably mounted thereon to extend therefrom forstabilizing said booster section relative to said main missile sectionwhile said two sections are coupled in flight, a main missile sectionrocket engine mounted within said aft body portion for sustaining theflight thereof, a booster rocket engine mounted Within said boostersection for initially boosting said missile in flight and including acombustion chamber and a thrust nozzle at the rear of said boostersection, control means operable automatically in response to subsidenceof gas pressure within said combustion chamber to uncouple said mainmissile and booster sections, and control means operable automatically.upon uncoupling of said main missile and booster sections to initiatefiring and operation of said main missile rocket engine. 7

6. In an air missile, the combination comprising a cylindrical body oflongitudinally sectionalized form including a main missile component anda flight booster component, rupturable means detachably connecting saidflight booster component to said main missile component, said mainmissile component comprising separate fore and aft and intermediate bodyportions detachably interconnected for quick field assembly,controllable flight guide flaps and fixed target seeking antenna devicesdetachably mounted on said fore body portion, fixed fin and movable flaptype flight path control devices mounted on said aft body portion forcooperation with said first men- .ucnea flight guide flaps to guide saidmain missile component in flight, fixed fin type flight guidance vanesdetachably mounted on said flight booster component adjacent the rearend thereofand extending therefrom for stabilizing said flight boostercomponent relative to said missile component while said two componentsare Z main body section and a booster flight section, a multi- ,7 partyoke detachably connecting said booster flight section to said main bodysection, a plurality of explosive bolt means interconnecting the partsof said yoke, said booster flight section having mounted therein arocket engine including a combustion chamber developing gas pressuretherein when in operation, detonator means op- :erably associated withsaid explosive bolt means for initiating explosion thereof, anddetonator'control means responsive to loss of pressure in saidcombustion chamber to cause explosive disruption ofsaid bolt means, saidyoke being adapted to disengage said main body and a booster flightsections upon disruption of any of said bolt means.

8. In an air missile, a multi-part casing comprising a main body sectionand a booster flight section, means ineluding a plurality of explosivebolt means detachably connecting said booster flight section to saidmain body "section, said booster flight section having mounted therein arocket engine including a'combustion chamber developing gas pressuretherein when in operation, detonator 1 means operably associated withsaid bolt means for initiating explosion thereof, and detonator controlmeans responsive to loss of pressure in said combustion chamber to acause explosive disruption of said bolt means, said main bodyand boosterflight sections being adapted to disengage 'fupon disruption of any ofsaid bolt means.

" 9. In an air missile construction, a generally cylindrically shapedbody, a flight control vane structure adjacent one end of said body,said vane structure comprising a first pair of diametrically opposedfixed fins extending radially of said body in a first plane, a secondpair of diametrically opposed fixed fins extending from opposite sidesof said body radially therefrom in'a second plane substantially normalto said firstmentioned plane, flight control flaps hingedly mounted uponthe trailing edge pore tions of said fins, torque shafts interconnectingeach pair of said flaps for controlling the pivoting thereof, saidtorque shafts having their'axes of rotation intersecting and both ofsaid shafts being locally deformed in the region of said intersecting toavoid each other and to permit 1'0 tations thereof, within limits, forflap operating movements of said shafts;

10. In an air missile construction, an airframe, a flight control vanestructure adjacent one end of said frame, said vane structure comprisinga first pair of diametrically opposed flight control-flaps hingedlymounted upon and extending radially of said frame in a first plane, asecond pair of diametrically opposed flight control flaps hingedlymounted upon and extending from opposite sides of said body radiallytherefrom in a second plane substantially normal to said first mentionedplane, a pair of torque shafts, one of said shafts interconnecting saidfirst pair of said flaps and the other of said shafts'interconnectingsaid second pair of said flaps for controlling the pivoting thereof,said torque shafts having their axes of rotation inter secting, and eachof said shafts being cut away to its axis of rotation and beveled onopposite sides thereof in the region of said intersecting to avoidinterferences with each other and to permit rotations thereof, within.limits, for flap operating movements of said shafts.

References Cited in the file of this patent UNITED STATES PATENTS1,547,329 Jones July 28, 1925 2,413,621 Hammond Dec. 31, 1946 2,414,398.Rous Jan. 28, '1947 2,644,396 Billman -5 Jilly 7, 1953 Schmid Oct. 6,1953 OTHER REFERENCES Popular Science, Antennas Go Into Hiding, October1949, page 169.

1. IN AN AIR MISSILE CONSTRUCTION A STREAMLINE SHAPED BODY, A FLIGHTCONTROL VANE STRUCTURE COMPRISING A FIXED FIN EXTENDING RADIALLY OF SAIDBODY, A CHANNEL SECTIONED BRACKET EMBRACING AND FIXED TO THE OUTBOARDEND OF SAID FIN AND EXTENDING REARWARDLY THEREOF, A TARGET SEEKINGANTENNA DEVICE OF ELONGATED FORM FIXED TO THE OUTER SIDE PORTION OF SAIDBRACKET TO EXTEND PARALLEL TO SAID BODY, A BEARING BLOCK DETACHABLYBOLTED TO SAID BRACKET, AND HAVING A HINGE PIN EXTENDING INWARDLYTHEREFROM, A STUB SHAFT ROTATABLY MOUNTED WITHIN SAID BODY AND CONNECTEDTHEREIN TO A FLAP CONTROL DEVICE AND EXTENDING OUTWARDLY THEREFROM, ANDA FLIGHT CONTROL FLAP FIXED AT ONE END TO SAID HINGE PIN AND DETACHABLYBOLTED TO SAID STUB SHAFT.